Stator vane segment for aircraft engine and method of producing the same

A method of manufacturing a stator for a turbine of an aircraft engine, the stator having an inner shroud, an outer shroud, and airfoils extending from the inner shroud to the outer shroud, the method comprising:

• obtaining raw vane segments including inner shroud raw segments, outer shroud raw segments, and airfoils extending from the inner shroud raw segments to the outer shroud raw segments, the inner shroud raw segments and the outer shroud raw segments having opposite inner and outer lateral faces facing baseline directions defining baseline angles with the central axis of the stator, chords of the airfoils defining raw angles with a central axis of the stator;
• determining a desired angle defined between the chords of the airfoils and the central axis of the stator based on a desired throat area defined between adjacent airfoils;
• removing material from the inner and outer lateral faces of the inner shroud raw segments and the outer shroud raw segments based on the desired angle to change the baseline directions of the inner and outer lateral faces to obtain vane segments having inner shroud segments of the inner shroud and outer shroud segments of the outer shrouds, including changing the raw angles defined between the chords of the airfoil and the central axis to the desired angle by changing angles defined between the central axis and directions normal to the inner and outer lateral faces;
• and
• assembling the vane segments together to obtain the stator by disposing the vane segments circumferentially around the central axis.